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The Compressible Flow Past Various Plane Profiles Near Sonic VelocityIn an earlier report UM No.1117 by Gothert,the single-source method was applied to the compressible flow around circles, ellipses, lunes, and around an elongated body of revolution at different Mach numbers and the results compared as far as possible with the calculations by Lamla ad Busemann. Essentially, it was found that with favorable source arrangement the single-source method is in good agreement with the calculations of the same degree of approximation by.Lamla and Busemann. Near sonic velocity the number of steps must be increased considerably in order to sufficiently approximate the adiabatic curve. After exceeding a certain Mach number where local supersonic fields occur already, it was no longer possible, in spite of the substantially increased number of steps, to obtain a systematic solution because the calculation diverged. This result,was interpreted to mean that above this point of divergence the symmetrical type of flow ceases to exist and changes into the unsymmetrical type characterized by compressibility shocks.
Document ID
20050031088
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Goethert, B. (Zentrale fuer Wissenschaftliches Berichtswesen Berlin, Germany)
Kawalki, K. H. (Zentrale fuer Wissenschaftliches Berichtswesen Berlin, Germany)
Date Acquired
August 22, 2013
Publication Date
January 13, 1949
Publication Information
Publication: Untersuchungen und Mitteilurgen
Issue: 1471
Subject Category
Aerodynamics
Report/Patent Number
NACA-TM-1203
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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